Assessment degree of disequilibrium gase in supersonic flows
https://doi.org/10.18384/2949-5067-2024-1-48-55
Abstract
Aim. The purpose of this work was to assess the applicability of first approximation models for describing the flow around surfaces of high curvature (sharp edges).
Methodology.The work used methods of molecular kinetic theory of gases. To numerically solve integral-differential equations, a model kinetic equation of polyatomic gases was used.
Results. The maximum degree of gas disequilibrium medium was calculated in the problem on profile of flat shock wave and in the problem of flow around a thin plate for a diatomic gas in the range of Mach numbers from 2 to 8. An almost twofold increase in the degree of disequilibrium in the region of the plate nose was obtained compared with nonequilibrium on the profile of a plane shock wave.
Research implications. The results obtained confirm the well-known position about the physical inadequacy of first-approximation models, in particular the Navier – Stokes – Fourier (NSF) model, when describing flows around sharp edges. Results can be used to develop flow models aimed at solving this problem.
Keywords
molecular kinetic theory of gases,
model kinetic equation,
dynamic nonequilibrium,
sharp edge,
shock wave
Supporting agencies: This work was financially supported by the Ministry of Education and Science of the Russian Federation, project No. FSFF-2023-0008.
About the Author
E. K. Krasavin
Moscow Aviation Institute (National Research University)
Russian Federation
Russian Federation
Egor E. Krasavin – Postgraduate Student, Department of Aerodynamics, dynamics and control of aircraft
ulitsa Volokolamskoe shosse 4, Moscow 125993
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